Position controller
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[0034]Hereinafter, embodiments will be described with reference to the drawings.
[0035]FIG. 1 is a skeleton diagram of a drive mechanism-integrated power generator 1 according to the embodiment. As shown in FIG. 1, the integrated drive generator (hereinafter referral to as “IDG”) 1 is used as an AC power supply for an aircraft. At the time of startup of the IDG1, even if rotational power of an engine rotary shaft of an aircraft starts to be transmitted to the IDG1, until the IDG1 can be stably operated, electrical components in the aircraft are driven by an auxiliary power supply that is different from the IDG1 (for example, an external generator or an auxiliary generator). When the IDG1 can be stably operated, the power supply of the electrical components is switched from the auxiliary power supply to the IDG1. Since the IDG1 is used as a main power supply of the aircraft, the power supply is switched from the auxiliary power supply to the IDG1 before takeoff.
[0036]The IDG 1 include...
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